CN108860660B - Tension compensation device of flexible compression release mechanism - Google Patents
Tension compensation device of flexible compression release mechanism Download PDFInfo
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- CN108860660B CN108860660B CN201810705962.5A CN201810705962A CN108860660B CN 108860660 B CN108860660 B CN 108860660B CN 201810705962 A CN201810705962 A CN 201810705962A CN 108860660 B CN108860660 B CN 108860660B
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- tension
- tension cable
- release mechanism
- disc spring
- end cover
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The invention discloses a tension compensation device of a flexible compression release mechanism, which comprises a limit bushing, a disc spring assembly, a spiral spring and a movable end cover, wherein the device is arranged between a tension cable assembly and a compression seat of the flexible compression release mechanism, the disc spring assembly and the spiral spring are arranged between the limit bushing and the movable end cover, the limit bushing is fixed to the compression seat, the tension cable assembly penetrates through an inner hole of the movable end cover, the disc spring assembly and the spiral spring are compressed when the tension cable is compressed to the compression seat by a connecting piece, creep relaxation occurs when the tension cable is tensioned for a long time, the disc spring assembly rebounds for compensating tension in a small amplitude, and when the tension cable is cut off, the tension cable is extended, the spiral spring rebounds for compensating tension in a large amplitude, and the like. The tension compensation device can realize tension compensation provided by the tension cable in the flexible compression release mechanism of the spacecraft, and has the advantages of simple structure, good assembly process and obvious anti-loosening effect.
Description
Technical Field
The invention relates to a tension compensation device of a spacecraft, in particular to a tension compensation device of a flexible compression release mechanism.
Background
The hot knife used for releasing the restraint in the flexible pressing and releasing mechanism can be repeatedly utilized, thereby reducing the cost and avoiding the potential safety hazard of initiating explosive devices in the test, simultaneously reducing the impact and pollution to the spacecraft possibly generated in the releasing process, further improving the reliability, reducing the development cost and the development risk, better meeting the requirements of future satellite tasks on the pressing and releasing mechanism, in the launching stage, the unfolding mechanism is fixed on the side surface of the body through the tension cable assembly, after the spacecraft is in orbit, the hot knife cuts off the tension cable according to instructions, the restraint between the release bracket and the pressing seat is released, the unfolding mechanism can be freely unfolded, in order to adapt to the mechanical conditions in the launching stage, the flexible pressing and releasing mechanism needs to have a certain tension force when being installed, wherein the tension cable assembly is a tension force source, and the mechanism is loosened due to the time interval between installation and launching, or loosened due to overload, the tension is reduced, a tension test of a flexible compression release mechanism of a certain type is taken as an example, a pre-tightening load is applied for 1000N during installation, the pre-tightening load is reduced to 200-300N after vibration, in addition, when a hot knife starts to work, a tension cable is gradually fused and slightly extends, the tension cable also becomes loose, the quick cutting is not facilitated, and even the failure that the tension cable cannot be cut occurs.
Disclosure of Invention
The invention aims to solve the technical problem of providing a tension compensation device of a flexible compression release mechanism, which can realize tension compensation provided by a tension cable in the flexible compression release mechanism of a spacecraft, and has the advantages of simple structure, good assembly process and obvious anti-loosening effect.
The invention solves the technical problems through the following technical scheme: the utility model provides a tension compensation arrangement of flexible type pressure release mechanism, a serial communication port, it includes limit bushing, the dish spring subassembly, coil spring, the activity end cover, the device installs in the flexible type and compresses tightly between the tension cable subassembly of release mechanism and the seat that compresses tightly, dish spring subassembly and coil spring are between limit bushing and activity end cover, limit bushing is fixed to compressing tightly the seat, the tension cable subassembly penetrates from the hole of activity end cover, the tension cable will be compressed tightly to compressing tightly the seat by the connecting piece when, dish spring subassembly and coil spring are compressed, when the long-term tensioning of tension cable appears creep relaxation, the little width of cloth spring-back compensation tension of dish spring subassembly, when the incision appears at the cutting-off process in the tension cable, when leading to the tension cable to extend, by coil spring by a wide margin compensation tension, guarantee that the tension cable is in the tensioning.
Preferably, the disc spring assembly and the helical spring are in a parallel relationship, with the respective parts being mounted coaxially.
Preferably, the ratio of the thickness of the disc spring in the disc spring assembly to the free deformation height is zero at one point, five to two points, and the maximum working stroke of the disc spring assembly is not more than zero point, six times of the free deformation height.
Preferably, the movable end cover is in clearance fit with the shaft hole of the limiting bush, so that the movable end cover can freely move up and down, the top of the limiting bush is provided with a mechanical limiting column, and the mechanical limiting column prevents the disc spring assembly from being crushed under the overload condition.
The positive progress effects of the invention are as follows: the flexible compression release mechanism is provided with tension compensation within the whole service life range, under the compression state, the larger tension of the tension cable can improve the load weight of the connected piece, the flexible compression release mechanism is suitable for larger on-track launching loads, the action time of the flexible compression release mechanism is shortened in the release process, and the reliability of the mechanism is improved.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic view of the pressing state of the flexible pressing release mechanism according to the present invention.
FIG. 3 is a schematic diagram of the flexible compression release mechanism of the present invention, wherein the compression release mechanism is in a compressed state for a long time, and the tension cable is subjected to a creep process and compensated by the disc spring assembly.
FIG. 4 is a schematic diagram of the flexible compression release mechanism of the present invention, illustrating the coil spring compensating the tension during the release process.
Detailed Description
The following provides a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings.
As shown in fig. 1 to 4, the tension compensation device of the flexible compression release mechanism of the invention comprises a limit bushing 5, a disc spring assembly 6, a spiral spring 7 and a movable end cover 8, the device is installed between a tension cable assembly 3 and a compression seat 2 of the flexible compression release mechanism, the disc spring assembly and the spiral spring are arranged between the limit bushing and the movable end cover, the limit bushing is fixed to the compression seat, the tension cable assembly penetrates through an inner hole of the movable end cover, when the tension cable is compressed to the compression seat by a connecting piece 1, the disc spring assembly and the spiral spring are compressed, when the tension cable is tensioned for a long time and has creep relaxation, the disc spring assembly rebounds for compensating tension in a small amplitude, when a cut occurs in the cutting process of the tension cable, the tension cable is extended, the spiral spring rebounds for compensating tension in a large amplitude, and the tension cable is ensured to be.
The disc spring assembly 6 and the spiral spring 7 are connected in parallel, and all parts are coaxially mounted, so that the disc spring assembly is convenient to mount.
The ratio of the thickness of the disc spring in the disc spring assembly 6 to the free deformation height is zero at one point, five to two points, and the maximum working stroke of the disc spring assembly is not more than zero point, six times of the free deformation height, so that the precision is improved.
The movable end cover 8 is in clearance fit with the shaft hole of the limiting bush 5, so that the movable end cover can freely move up and down, the top of the limiting bush is provided with a mechanical limiting column 9, and the mechanical limiting column 9 prevents the disc spring assembly 6 from being crushed under the overload condition.
The working principle of the invention is as follows: a tension compensation device is arranged between the tension cable assembly and the compression seat, compensation force is derived from the disc spring assembly and the spiral spring, and creep relaxation of the tension cable is compensated by using the advantages of small stroke, large bearing capacity and high rigidity of the disc spring assembly in a long-term compression state; after the spacecraft entered the orbit, the flexible type compresses tightly release and is at the release in-process, because the incision rope further extends, surpass dish spring working range, it is in the tensioning state to keep coil spring to provide the tension cable, be favorable to the tension cable to be cut off fast, spacing bush and activity end cover provide the device respectively and compress tightly the seat, the installation interface of tension cable subassembly, spacing bush and activity end cover shaft hole cooperation, can the axial activity, the dish spring subassembly, coil spring installs in parallel between spacing bush and activity end cover, in order to improve working stroke, the dish spring subassembly comprises 2 ~ 4 dish springs in series connection, tension cable diameter 4mm according to the tension cable subassembly, the following design is carried out to the rated load 750N requirement: firstly, a pressing seat provides an installation space with the diameter of 58mm and the depth of 22 mm; secondly, the disc spring assembly is installed by connecting 3 disc springs in series, the disc spring is made of 60SiMnA, the inner diameter is 20.4mm, the outer diameter is 40mm, the thickness is 0.8-0.9 mm, the total height of the disc springs is 6.5-7.0 mm, and the maximum compression stroke is 2.4-2.6 mm; thirdly, the spiral spring is made of 60SiMnA, the middle diameter is 45mm, the diameter of the coil is 1.5-2.0 mm, and the two ends of the spiral spring are flattened, the free length is 25mm, the compression state is compressed by 10mm, and the tension cable is guaranteed to be compressed all the time in the whole releasing process; and fourthly, coating molybdenum disulfide serving as a solid lubricant on the matching surface of the bushing and the movable end cover, wherein the thickness of the coating is 10 mu m, so that vacuum cold welding is prevented, coating molybdenum disulfide serving as a solid lubricant on the contact surface of the limiting bushing and the disc spring assembly and the contact surface of the movable end cover and the disc spring assembly, and coating the thickness of the coating is 10 mu m.
In conclusion, the tension compensation provided by the tension cable in the flexible compression and release mechanism of the spacecraft can be realized, the structure is simple, the assembly process is good, and the anti-loosening effect is obvious.
The above embodiments are described in further detail to solve the technical problems, technical solutions and advantages of the present invention, and it should be understood that the above embodiments are only examples of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The utility model provides a tension compensation arrangement of flexible type pressure release mechanism, a serial communication port, it includes limit bushing, the dish spring subassembly, coil spring, the activity end cover, the device installs in the flexible type and compresses tightly between the tension cable subassembly of release mechanism and the seat that compresses tightly, dish spring subassembly and coil spring are between limit bushing and activity end cover, limit bushing is fixed to compressing tightly the seat, the tension cable subassembly penetrates from the hole of activity end cover, the tension cable will be compressed tightly to compressing tightly the seat by the connecting piece when, dish spring subassembly and coil spring are compressed, when the long-term tensioning of tension cable appears creep relaxation, the little width of cloth spring-back compensation tension of dish spring subassembly, when the incision appears at the cutting-off process in the tension cable, when leading to the tension cable to extend, by coil spring by a wide margin compensation tension, guarantee that the tension cable is in the tensioning.
2. The tension compensating apparatus of a flexible compression release mechanism of claim 1, wherein the disc spring assembly and the coil spring are in a parallel relationship, with the components being coaxially mounted.
3. The tension compensating apparatus of claim 1, wherein the ratio of the thickness of the disc spring to the free deflection height of the disc spring assembly is zero at one point, five to two points, and the maximum stroke of the disc spring assembly is no greater than zero, six times the free deflection height.
4. The tension compensating device of a flexible compression release mechanism as claimed in claim 1, wherein the movable end cap is in clearance fit with the shaft hole of the limiting bush to facilitate free up-and-down movement, and a mechanical limiting post is disposed on the top of the limiting bush to prevent the disc spring assembly from collapsing under overload condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705962.5A CN108860660B (en) | 2018-06-26 | 2018-06-26 | Tension compensation device of flexible compression release mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705962.5A CN108860660B (en) | 2018-06-26 | 2018-06-26 | Tension compensation device of flexible compression release mechanism |
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| Publication Number | Publication Date |
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| CN108860660A CN108860660A (en) | 2018-11-23 |
| CN108860660B true CN108860660B (en) | 2020-05-29 |
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| CN201810705962.5A Active CN108860660B (en) | 2018-06-26 | 2018-06-26 | Tension compensation device of flexible compression release mechanism |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625328A (en) * | 2018-12-12 | 2019-04-16 | 上海卫星装备研究所 | Fuse Type compresses release device |
| CN111645881B (en) * | 2020-05-28 | 2023-09-08 | 上海航天设备制造总厂有限公司 | Load connection and unlocking capability test tool and method |
| CN111969291B (en) * | 2020-08-18 | 2022-11-22 | 天津航天机电设备研究所 | Satellite antenna pressing and unlocking device and using method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6119984A (en) * | 1999-07-16 | 2000-09-19 | Swales Aerospace | Low shock anti-friction release device |
| EP0738656B1 (en) * | 1995-04-19 | 2000-10-25 | Alcatel | Retract control device of a movable structure |
| CN105659761B (en) * | 2008-11-12 | 2013-02-27 | 北京空间飞行器总体设计部 | Spacecraft equipment supporting component release stopping means |
| CN204642167U (en) * | 2014-11-25 | 2015-09-16 | 上海宇航系统工程研究所 | Locking releasing device can be repeated in a kind of space |
| US9964099B2 (en) * | 2015-03-31 | 2018-05-08 | Aerea S.P.A. | Device for holding and deploying apparatus for use in space |
-
2018
- 2018-06-26 CN CN201810705962.5A patent/CN108860660B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0738656B1 (en) * | 1995-04-19 | 2000-10-25 | Alcatel | Retract control device of a movable structure |
| US6119984A (en) * | 1999-07-16 | 2000-09-19 | Swales Aerospace | Low shock anti-friction release device |
| CN105659761B (en) * | 2008-11-12 | 2013-02-27 | 北京空间飞行器总体设计部 | Spacecraft equipment supporting component release stopping means |
| CN204642167U (en) * | 2014-11-25 | 2015-09-16 | 上海宇航系统工程研究所 | Locking releasing device can be repeated in a kind of space |
| US9964099B2 (en) * | 2015-03-31 | 2018-05-08 | Aerea S.P.A. | Device for holding and deploying apparatus for use in space |
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| CN108860660A (en) | 2018-11-23 |
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